Application of blade tip clearance measurement technology on centrifugal compressor test rig

被引：0
作者：
Li L. [1 ]
Zhang J. [2 ]
Cai X. [1 ]
机构：
[1] Compressor Research Department, Hunan Aviation Powerplant Research Institute, Aero Engine(Group) Corporation of China, Zhuzhou, 412002, Hunan
[2] Measurement and Test Technology Research Department, Hunan Aviation Powerplant Research Institute, Aero Engine (Group) Corporation of China, Zhuzhou, 412002, Hunan
来源：
| 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 32期
关键词：
Blade tip clearance; Centrifugal impeller; Clearance measurement technology; Compressor; Test rig;
D O I：
10.13224/j.cnki.jasp.2017.09.026
中图分类号：
学科分类号：
摘要：
Each part consisted of the capacitive blade tip clearance measurement system was introduced. The install method and check method of blade tip clearance measurement on centrifugal compressor test rig were mentioned. While the blade tip clearance on centrifugal compressor test rig was monitored in real time, the blade tip clearance decreased with the increase of speed on inlet, middle and outlet sections. The test safety and test rig integrity were ensured. Relationship between blade tip clearance and speed is able to help to further reduce cold blade tip clearance and gain the optional flow path of centrifugal impeller tip and impeller cover. The application of blade tip clearance measurement technology on centrifugal compressor test rig can help ensure the optimal clearance and also provides important data support. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：2260 / 2264
页数：4
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